Exterior aircraft display system

ABSTRACT

A method and apparatus for displaying information is presented. The information is sent from a number of sources to a display unit. The information is displayed through pixels located in the display unit. Heat is transferred in the display unit through a conductive path.

CROSS-REFERENCE TO RELATED APPLICATION

This application is a continuation-in-part of prior U.S. patentapplication Ser. No. 13/603,040, filed Sep. 4, 2012, and entitled“Exterior Aircraft Display System,” which is incorporated herein byreference in its entirety.

BACKGROUND INFORMATION

1. Field

The present disclosure relates generally to aircraft and, in particular,to displaying information on an aircraft. Still more particularly, thepresent disclosure relates to a method and apparatus for displayinginformation on the exterior of an aircraft.

2. Background

Advertisements and other messages are typically placed in advertisingspaces in fixed locations. Advertisements are commonly found onbillboards, buildings, and other structures. Advertisers have includedother systems, other than those in fixed locations, for increasing thevisibility of advertisements and other messages.

For example, advertisements are often placed on moving vehicles. Thesevehicles include buses, taxicabs, airplanes, and other suitable types ofvehicles. In some cases, trucks have been used solely for the purpose ofacting as a mobile billboard. With advertisements on vehicles, theseadvertisements can be seen in many more areas than may otherwise bepossible based on restrictions or costs for more traditional types ofadvertisements.

For example, advertisements may be painted on the surface of anaircraft. In other cases, the advertisements may be placed onto thesurface of an aircraft in the form of an appliqué. These types ofadvertisements, however, are static and cannot be easily changed on anaircraft. As a result, when the aircraft is used in different locations,the advertisements on an aircraft may not be as effective for aparticular audience that may view the advertisements in those one ormore locations. Therefore, it would be desirable to have a method andapparatus that takes into account at least some of the issues discussedabove, as well as other possible issues.

SUMMARY

In one illustrative embodiment, an apparatus comprises pixels, aprotective layer associated with the pixels, and a conductive path inthe protective layer that transfers heat. The protective layer issubstantially transparent in areas over the pixels. The pixels, theprotective layer, and the conductive path form a display unit for anaircraft.

In another illustrative embodiment, a method for displaying informationis presented. The information is sent from a number of sources to adisplay unit. The information is displayed through pixels located in thedisplay unit. Heat is transferred in the display unit through aconductive path.

The features and functions can be achieved independently in variousembodiments of the present disclosure or may be combined in yet otherembodiments in which further details can be seen with reference to thefollowing description and drawings.

BRIEF DESCRIPTION OF THE DRAWINGS

The novel features believed characteristic of the illustrativeembodiments are set forth in the appended claims. The illustrativeembodiments, however, as well as a preferred mode of use, furtherobjectives and features thereof, will best be understood by reference tothe following detailed description of an illustrative embodiment of thepresent disclosure when read in conjunction with the accompanyingdrawings, wherein:

FIG. 1 is an illustration of a block diagram of an information displayenvironment in accordance with an illustrative embodiment;

FIG. 2 is an illustration of a block diagram of a display unit inaccordance with an illustrative embodiment;

FIG. 3 is an illustration of an aircraft in accordance with anillustrative embodiment;

FIG. 4 is an illustration of a portion of the second wing of theaircraft in FIG. 3 with the second winglet in accordance with anillustrative embodiment;

FIG. 5 is an illustration of another view of a portion of the secondwing of the aircraft in FIG. 3 with the second winglet in accordancewith an illustrative embodiment;

FIG. 6 is an illustration of the tail section of the aircraft in FIG. 3in accordance with an illustrative embodiment;

FIG. 7 is an illustration of another portion of the aircraft in FIG. 3in accordance with an illustrative embodiment;

FIG. 8 is an illustration of another portion of the aircraft in FIG. 3in accordance with an illustrative embodiment;

FIG. 9 is an illustration of a first display unit on a first horizontalstabilizer and a second display unit on a second horizontal stabilizerof the aircraft in FIG. 3 in accordance with an illustrative embodiment;

FIG. 10 is an illustration of a cross-sectional view of a verticalstabilizer of the aircraft in FIG. 3 in accordance with an illustrativeembodiment;

FIG. 11 is an exploded perspective view of the display unit on thevertical stabilizer of the aircraft in FIG. 3 in accordance with anillustrative embodiment;

FIG. 12 is an illustration of another implementation for the displayunit on the vertical stabilizer of the aircraft in FIG. 3 in accordancewith an illustrative embodiment;

FIG. 13 is an illustration of a block diagram of a display unit inaccordance with an illustrative embodiment;

FIG. 14 is an illustration of a display unit with a cooling system inaccordance with an illustrative embodiment;

FIG. 15 is an illustration of a cross-sectional view of a display unitwith a cooling system in accordance with an illustrative embodiment;

FIG. 16 is an illustration of another cross-sectional view of a displayunit with a cooling system in accordance with an illustrativeembodiment;

FIG. 17 is an illustration of a display unit in accordance with anillustrative embodiment;

FIG. 18 is an illustration of a cross-sectional view of a display systemin accordance with an illustrative embodiment;

FIG. 19 is an illustration of another cross-sectional view of a displayunit with a cooling system in accordance with an illustrativeembodiment;

FIG. 20 is an illustration of another cross-sectional view of a displayunit with a cooling system in accordance with an illustrativeembodiment;

FIG. 21 is an illustration of another cross-sectional view of a displayunit with a cooling system in accordance with an illustrativeembodiment;

FIG. 22 is an illustration of a portion of a display unit in accordancewith an illustrative embodiment;

FIG. 23 is an illustration of a flowchart of a process for displayingthe information on the exterior surface of the aircraft in FIG. 1 inaccordance with an illustrative embodiment;

FIG. 24 is an illustration of a flowchart of a process for selecting theimage in FIG. 2 using the information in FIG. 1 in accordance with anillustrative embodiment;

FIG. 25 is an illustration of a flowchart of a process for displayinginformation in accordance with an illustrative embodiment;

FIG. 26 is an illustration of a block diagram of a data processingsystem in accordance with an illustrative embodiment;

FIG. 27 is an illustration of a block diagram of an aircraftmanufacturing and service method in accordance with an illustrativeembodiment; and

FIG. 28 is an illustration of a block diagram of an aircraft in which anillustrative embodiment may be implemented.

DETAILED DESCRIPTION

The illustrative embodiments recognize and take into account one or moredifferent considerations. For example, the illustrative embodimentsrecognize and take into account that one manner in which dynamicdisplays may be provided for the exterior of an aircraft is through theuse of projectors. These projectors may use bright lights or lasers todisplay information on the exterior surface of the aircraft.

The illustrative embodiments recognize and take into account, however,that the locations where projectors may be placed on an aircraft toproject information on the exterior surface of an aircraft may belimited based on design, safety, and other considerations with respectto the aircraft. As a result, the locations of these display systems mayreduce the quality of the image in which the information is displayed.

Further, in addition to constraints on locations where the projectorscan be placed, the exterior surface of the aircraft may includeartifacts or may have coatings that may reduce the quality of the imagethat may be displayed on the exterior surface of the aircraft. Also, thedisplay of information on the exterior surface of the aircraft may behindered during some environmental conditions, such as rain, fog, dust,or other undesirable environmental conditions.

Thus, the illustrative embodiments provide a method and apparatus fordisplaying information on the exterior surface of an aircraft. In oneillustrative embodiment, an apparatus comprises a support structure foran aircraft and a display panel associated with the support structure onthe exterior of the aircraft. The display panel is configured to displayinformation on the display panel on the exterior surface of theaircraft.

With reference now to the figures and, in particular, with reference toFIG. 1, an illustration of a block diagram of an information displayenvironment is depicted in accordance with an illustrative embodiment.In this illustrative example, an information display environment 100includes a vehicle 102 in the form of an aircraft 104.

In this illustrative example, a display system 106 may comprise adisplay control system 110, a number of display units 116, and a heattransfer system 134. As used herein, a “number of” when used withreference to items means one or more items. For example, a number ofdisplay units 116 is one or more display units 116.

A computer system 108 in the aircraft 104 is configured to interfacewith different systems on the aircraft 104. As depicted, the computersystem 108 comprises a number of computers and is located in theaircraft 104. For example, the computer system 108 may include computersfor a navigation system, an engine indications and crew alerting system,an in-flight entertainment system, a terrain and ground featureinteractive passenger application, and other computers for othersuitable types of systems. In these illustrative examples, the computersystem 108 is in communication with the display system 106.

As depicted, a display module 112 may comprise at least one of aprocessor unit or a computer in the computer system 108. The displaymodule 112 may receive information 114, identify information 114,generate information 114, or some combination thereof. The displaymodule 112 may send the information 114 to the display system 106 fordisplay on the exterior surface 118 of the aircraft 104 by the number ofdisplay units 116. In these illustrative examples, information 114 maybe displayed on the exterior surface 118 of the aircraft 104 via thedisplay module 112.

Additionally, one or more of display units 116 may be located oninterior surface 117 of aircraft 104. Information 114 also may bedisplayed to passengers, crew members, and other people located ininterior surface 117 of aircraft 104. For example, display units 116 maybe located in a passenger cabin, a galley, a doorway, or some othersuitable location on interior surface 117 of aircraft 104.

In these illustrative examples, the display module 112 may beimplemented using hardware, software, or a combination of the two. Whensoftware is used, the operations performed by the display module 112 maybe implemented in program code configured to be run on a processor unit.When hardware is employed to implement the display module 112, thehardware may include circuits that operate to perform the operations inthe display module 112.

In these illustrative examples, the hardware may take the form of acircuit system, an integrated circuit, an application specificintegrated circuit (ASIC), a programmable logic device, or some othersuitable type of hardware configured to perform a number of operations.With a programmable logic device, the device is configured to performthe number of operations. The device may be reconfigured at a later timeor may be permanently configured to perform the number of operations.

Examples of programmable logic devices include, for example, aprogrammable logic array, a programmable array logic, a fieldprogrammable logic array, a field programmable gate array, and othersuitable hardware devices. Additionally, the processes may beimplemented in organic components integrated with inorganic componentsand/or may be comprised entirely of organic components excluding a humanbeing. For example, the processes may be implemented as circuits inorganic semiconductors.

In these illustrative examples, the information 114 may be used togenerate images 120 for display by the number of the display units 116in the display system 106 on the exterior surface 118 of the aircraft104. In this illustrative example, images 120 may be generated byvarious components. For example, the display module 112, the displaycontrol system 110, the number of the display units 116, or somecombination thereof may generate the images 120 displayed by the numberof the display units 116 in the display system 106 on the exteriorsurface 118 of the aircraft 104 from the information 114. In some cases,the information 114 may include the images 120.

The generation of the images 120 for display on the number of displayunits 116 may be controlled using triggering events 122. The triggeringevents 122 may be periodic or non-periodic events and may be obtainedusing the information 114. In these illustrative examples, thetriggering events 122 include any information that may be used by thecomputer system 108 to determine when, how, and where the number ofdisplay units 116 display the images 120 on the exterior surface 118 ofthe aircraft 104.

For example, the triggering events 122 may include a phase of flight ofthe aircraft 104. Based on the phase of flight, the display module 112may select one or more of the images 120 for use in the display of theimages 120 on the exterior surface 118 of the aircraft 104 by the numberof display units 116. As another example, if a message is received fromthe airport at which the aircraft 104 is located, that message may beused to generate an image in the images 120 for display on the exteriorsurface 118 of the aircraft 104. For example, the message may refer to aresult of an athletic event that may be included in the images 120 thatare displayed on the exterior surface 118 of the aircraft 104.

Further, the triggering events 122 also may include an indication thatthe aircraft 104 is approaching an airport gate, beginning a taxiingphase, initiating engine start, initiating hydraulics pressurization, orother suitable information that may be used to select the images 120 fordisplay on the exterior surface 118 of the aircraft 104. The triggeringevents 122 also may include location specific information in theinformation 114 used by the display module 112. This location of theaircraft 104 may be used to identify advertising, logos, and/or othersuitable types of the information 114 that may be used to generate orselect the images 120.

As another example, the triggering events 122 may include thoseinitiated or selected by the operator 123. The operator 123 may be apilot or other crew member. The operator 123 also may be a ground crewmember in these illustrative examples. In yet another illustrativeexample, the triggering events 122 may be the activity of the operator123 in the cabin of the aircraft 104. The operator 123 may be a crewmember or a passenger in the cabin of the aircraft 104. In theseillustrative examples, the display system 106 may be controlledpartially or completely by the operator 123.

In these illustrative examples, the communication between componentssuch as the computer system 108 and the display system 106 may beperformed over existing communications links established using differenttypes of communications media. The communications media may include, forexample, without limitation, wires, fiber optic cables, wirelesscommunications links, and other suitable types of media. Thecommunications links may be unidirectional, bidirectional, or acombination of the two.

In these illustrative examples, the information 114 may take variousforms. For example, the information 114 may be selected from at leastone of a logo, a trademark, an advertisement, a tail number, safetyinformation, flight information, baggage claim information, ground crewinformation, gate information, a direction blinker, a navigation light,warning information, or other suitable types of information.

As used herein, the phrase “at least one of”, when used with a list ofitems, means different combinations of one or more of the listed itemsmay be used and only one of each item in the list may be needed. Forexample, “at least one of item A, item B, or item C” may include,without limitation, item A or item A and item B. This example also mayinclude item A, item B, and item C or item B and item C. In otherexamples, “at least one of” may be, for example, without limitation, twoof item A, one of item B, and ten of item C; four of item B and seven ofitem C; or other suitable combinations.

In these illustrative examples, the information 114 may originate fromdifferent sources onboard the aircraft 104, off of the aircraft 104, orsome combination thereof. For example, the information 114 may includeinformation about the airport, the city in which the airport is located,events occurring in the city in which the airport is located, or somecombination thereof.

When the information 114 originates within the aircraft 104, theinformation 114 may be received from a number of sources 124 in thecomputer system 108. The number of sources 124 may be at least one of anavigation source 126, an advertisement database 128, a media library130, or other suitable sources.

When the information 114 originates from the navigation source 126, theinformation 114 may include information about at least one of fuellevels, direction of travel of the aircraft 104, or other suitableinformation about the aircraft 104. The advertisement database 128 mayinclude information 114 such as images 120. The images 120 may be stillimages for an advertisement. In other examples, the images 120 may bepart of a video for an advertisement. The information 114 in the medialibrary 130 may be, for example, without limitation, information aboutthe airline, information about a destination location for a flight, andother suitable types of information.

In these illustrative examples, the display module 112 is configured tocontrol the display of the images 120 by the number of display units 116associated with the exterior surface 118 of the aircraft 104. When onecomponent is “associated” with another component, the association is aphysical association in the depicted examples. For example, a firstcomponent, the number of display units 116, may be considered to beassociated with a second component, the exterior surface 118 of theaircraft 104, by being secured to the second component, bonded to thesecond component, mounted to the second component, welded to the secondcomponent, fastened to the second component, and/or connected to thesecond component in some other suitable manner. The first component alsomay be connected to the second component using a third component. Thefirst component may also be considered to be associated with the secondcomponent by being formed or manufactured as part of and/or an extensionof the second component. For example, the display module 112 may selectthe information 114.

In these illustrative examples, the number of display units 116 isassociated with a number of support structures 132 on the exteriorsurface 118 of the aircraft 104. In these illustrative examples, thenumber of the display units 116 are associated with the exterior surface118 of the aircraft 104 such that the number of the display units 116are substantially flush to the exterior surface 118 of the aircraft 104.

In other words, if the exterior surface 118 of the aircraft 104 issubstantially flat, the number of display units 116 maintains thatsubstantially flat surface on the exterior surface 118 of the aircraft104. If the exterior surface 118 of the aircraft 104 has a curve, thenumber of display units 116 at that location has a similar curve suchthat a display unit, when associated with the exterior surface 118 ofthe aircraft 104, maintains that curve desired for the aircraft. In thismanner, aerodynamic properties of the aircraft 104 for the exteriorsurface 118 of aircraft 104 may remain at a desired level ofperformance.

The heat transfer system 134 is configured to transfer heat 136 withrespect to the number of display units 116. In other words, heat 136 maybe conducted away from the number of display units 116 or toward thenumber of display units 116 depending on the particular implementation.The heat transfer system 134 also may direct heat away from the displaysystem 106, the computer system 108, and other electronics within thenumber of display units 116.

For example, heat 136 may be conducted away from the number of displayunits 116 to provide cooling for the number of display units 116. Inother illustrative examples, heat 136 may be conducted toward the numberof display units 116 to provide heating if the number of display units116 are colder than desired. In this manner, the heat transfer system134 may provide a desired operating temperature for the number ofdisplay units 116.

The number of the display units 116 is associated with the aircraft 104in a manner that reduces undesired airflow 138 when the aircraft 104 isin flight. The undesired airflow 138 may result in an increase in theaerodynamic drag. For example, the number of the display units 116 maybe associated with the aircraft 104 in a manner such that the number ofthe display units 116 is substantially flush to the exterior surface 118of the aircraft 104.

Although the illustrative examples for an illustrative embodiment aredescribed with respect to the aircraft 104, an illustrative embodimentmay be applied to other types of platforms. The platform may be, forexample, a mobile platform, a stationary platform, a land-basedstructure, an aquatic-based structure, and a space-based structure. Morespecifically, the platform, may be a surface ship, a tank, a personnelcarrier, a train, a spacecraft, a space station, a satellite, asubmarine, an automobile, a power plant, a bridge, a dam, a house, amanufacturing facility, a building, and other suitable platforms.

With reference now to FIG. 2, an illustration of a block diagram of adisplay unit is depicted in accordance with an illustrative embodiment.The display unit 200 illustrated in this figure is an example of adisplay unit that may be used in the number of display units 116 in thedisplay system 106 for the aircraft 104 in FIG. 1.

In this illustrative example, the display unit 200 may include a displaypanel 202, a substantially transparent protective layer 204, a videocontroller 206, and a support structure 208. The display panel 202 is ahardware device that is configured to display the information 114 fromFIG. 1. In particular, the display panel 202 may display an image 210.The image 210 may be generated from the information 114 in FIG. 1. Thedisplay panel 202 may be embedded within the exterior surface 118 of theaircraft 104 in FIG. 1.

In this illustrative example, the display panel 202 may be implementedusing a number of different types of display technologies. For example,the display panel 202 may be selected from at least one of alight-emitting diode display, an organic light-emitting diode display, aplasma display, a quantum dot display, a liquid crystal display, orother suitable types of display devices.

Further, the display panel 202 may be a structural member of theairframe or skin. The display panel 202 may be located in at least oneof a fuselage, a wing, a winglet, a horizontal stabilizer, a verticalstabilizer, an engine housing, or in some other suitable location.Moreover, the display panel 202 may have portions or segments. Theseportions or segments of the display panel 202 may be logicallyseparated, or may display a number of different images substantiallyconcurrently without a physical separation.

In other words, different segments in the display panel 202 may havedifferent images. For example, the display panel 202 may have twosegments configured to display two different images substantiallyconcurrently. The display panel 202 may also display a contiguous imageacross each segment in the display panel 202.

In this manner the display unit 200 may display these two images or moreimages substantially concurrently without a physical separation in thedisplay panel 202. Of course, other numbers of images may be displayedin segments of the display panel 202 depending on the particularimplementation. In some illustrative examples, the display unit 200 mayhave one or more display panels in addition to the display panel 202that form the portions of segments for displaying images.

The substantially transparent protective layer 204 is configured to beplaced over the display panel 202. The substantially transparentprotective layer 204 is configured to protect the display panel 202 fromthe environment around the aircraft 104 in FIG. 1.

The substantially transparent protective layer 204 may take variousforms. For example, the substantially transparent protective layer 204may be comprised of a material selected from at least one of glass, apolycarbonate, a composite material or other suitable materials.Further, in these illustrative examples, the substantially transparentprotective layer 204 may have various properties such as polarization,filtering frequencies of light, and other suitable properties. In someillustrative examples, the substantially transparent protective layer204 may be a lens.

The video controller 206 is a hardware device configured to control theoperation of pixels 212 on the display panel 202 to display the image210 on the display panel 202. The video controller 206 may take variousforms. For example, the video controller 206 may be a graphics card, acomputer, video driver, a processor unit, or some other suitable device.The video controller 206 may also provide power for the pixels 212 inaddition to controlling the image 210 displayed on the display panel202.

The support structure 208 is configured to provide support for thedisplay panel 202. In these illustrative examples, the support structure208 may be a frame, a housing, or some other suitable type of structure.For example, the support structure 208 may be located in or selectedfrom at least one of a fuselage, a wing, a winglet, a horizontalstabilizer, a vertical stabilizer, an engine housing, or some othersuitable location. In some illustrative examples, the substantiallytransparent protective layer 204 may be considered all or part of thesupport structure 208 and/or a cooling system. In other illustrativeexamples, the substantially transparent protective layer 204 may beintegrated in the display panel 202.

In these illustrative examples, the video controller 206 may beassociated with the support structure 208. In other illustrativeexamples, the video controller 206 may be located in a separate locationfrom the support structure 208 and the display panel 202.

For example, the video controller 206 and the display panel 202 may bothbe in different locations in a winglet or wingtip of the aircraft 104 inFIG. 1. When the video controller 206 is in a separate location from thesupport structure 208 and the display panel 202, the video controller206 may be in communication with the display panel 202 using a wire, awireless communications link, an optical fiber, or some other suitablemedium. For example, the communications link may be made using a flatserial cable between the video controller 206 and the display panel 202for the display unit 200.

In these illustrative examples, the support structure 208 with thesubstantially transparent protective layer 204 is configured to beconnected to the aircraft 104 in a manner that reduces the undesiredairflow that may occur. As depicted, a heat conductor 214 is configuredto aid in providing a desired operating temperature 216 for the displaypanel 202 and other components in the display unit 200, the displaysystem 106 in FIG. 1, and the computer system 108 as required in otherillustrative examples.

The heat conductor 214 may transfer heat away from the display panel202, the display system 106, and the computer system 108 to maintain thedisplay panel 202 at the desired operating temperature 216. In otherillustrative examples, when the environment is colder than desired, theheat conductor 214 may transfer heat to the display panel 202 tomaintain the desired operating temperature 216 for the display panel202.

In these illustrative examples, the heat conductor 214 may beimplemented using any structure that is configured to conduct heat. Forexample, without limitation, the heat conductor 214 may be comprised ofa metal, a ceramic, a composite, and other suitable materials. The heatconductor 214 also may take various forms. For example, the heatconductor 214 may be a fin, a mesh, or some other suitable structurethat is configured to provide a path for heat transfer to the displaypanel 202, from the display panel 202, or some combination thereof.

In these illustrative examples, the heat conductor 214 may be thermallyconnected to the heat transfer system 134 in FIG. 1. In otherillustrative examples, the heat conductor 214 may form the heat transfersystem 134 in FIG. 1. Further, the heat conductor 214 may serve as anelectrical conductor as well as an electrical ground for components inthe display unit 200, the display system 106, the computer system 108,or other components in these illustrative examples. Moreover, the heatconductor 214 may be integrated as part of the aircraft structure.

The illustrations of the information display environment 100 in FIG. 1and example components for the display unit 200 in FIG. 2 are not meantto imply physical or architectural limitations to the manner in which anillustrative embodiment may be implemented. Other components in additionto or in place of the ones illustrated may be used. Some components maybe unnecessary. Also, the blocks are presented to illustrate somefunctional components. One or more of these blocks may be combined,divided, or combined and divided into different blocks when implementedin an illustrative embodiment.

For example, in some illustrative examples, the support structure 208may not be part of the display unit 200. Instead, the support structure208 may be a structure in the aircraft 104. For example, the supportstructure 208 may be the fuselage, a skin panel, or other structure inthe aircraft 104 in FIG. 1. In still other illustrative examples, thevideo controller 206 may be connected to the support structure 208 alongwith the display panel 202.

In another illustrative example, the computer system 108 may beintegrated with the display system 106 in FIG. 1. As another example,the computer system 108 may be integrated with the video controller 206.

In still another illustrative example, the information displayenvironment 100 in FIG. 1 may include a second aircraft with a seconddisplay system. The display system 106 in the aircraft 104 may displayinformation 114 in FIG. 1 in coordination with the display ofinformation by the second aircraft. For example, if the aircraft 104 andthe second aircraft are lined up by each other at gates or on a taxiway,the display of information 114 and/or animation of information 114 bythe aircraft 104 in FIG. 1 and the second aircraft may be coordinatedwith each other.

As another example, information 114 may be passed between multipleaircraft to be displayed on each aircraft in a rolling pattern such thatinformation 114 from one aircraft is then seen on a neighboringaircraft, and so on. In other words, parts or all of the sameinformation 114 may be displayed on different aircraft lined up at thegate in a time-coordinated or rolling manner such that viewers seeinformation 114 in a desired manner on multiple aircraft. Information114 may also be sent from or displayed upon aircraft to aircraft in aprogressive manner or in pulses, depending on the particularimplementation.

As another example, portions of the computer system 108 and theinformation 114 may be located in different locations in aircraft 104.For example, portions of the computer system 108 and the information 114may be located in an in-flight entertainment system in the aircraft 104.Also, the information 114 may be located in a location remote to theaircraft 104 and sent to the aircraft 104.

With reference now to FIG. 3, an illustration of an aircraft is depictedin accordance with an illustrative embodiment. In this depicted example,an aircraft 300 is an example of a physical implementation for theaircraft 104 shown in block form in FIG. 1.

In this illustrative example, the aircraft 300 has a first wing 302 anda second wing 304 attached to a fuselage 306. The aircraft 300 includesa first engine 308 attached to the first wing 302 and a second engine310 attached to the second wing 304.

The fuselage 306 has a nose section 312 and a tail section 314. A firsthorizontal stabilizer 316, a second horizontal stabilizer 318, and avertical stabilizer 320 are attached to the tail section 314 of thefuselage 306.

In these illustrative examples, display units 322, 324, 326, 328, 330,and 332 can be seen on the aircraft 300. The display units 322, 324,326, 328, 330, and 332 are examples of physical implementations for thenumber of display units 116 shown in block form in FIG. 1.

As depicted, the display units 322, 324, 326, 328, 330, and 332 may beimplemented using the display unit 200 in FIG. 2. As depicted, thedisplay units 322, 324, 326, 328, 330, and 332 are mounted on anexterior surface 340 of the aircraft 300. In particular, the displayunits 322, 324, 326, 328, 330, and 332 are mounted to be substantiallyflush to the exterior surface 340 of the aircraft 300. In other words,the display units 322, 324, 326, 328, 330, and 332 may be embeddedwithin the exterior surface 340 of the aircraft 300. In this manner,undesired airflow on the aircraft 300 may be reduced or avoided.

As depicted, a display unit 322 is located on the second wing 304. Adisplay unit 324 is located the fuselage 306. A display unit 326 islocated on the second engine 310. A display unit 328 is located on thefirst wing 302, while a display unit 330 is located on the verticalstabilizer 320.

In this illustrative example, the first wing 302 has a first winglet 336and the second wing 304 has a second winglet 338. In these illustrativeexamples, the first winglet 336 and the second winglet 338 are wing tipor wing surface structure extensions to the first wing 302 and thesecond wing 304, respectively.

The first winglet 336 and the second winglet 338 are configured to adddesirable aerodynamic performance. For example, the first winglet 336and the second winglet 338 may reduce lift induced drag and may provideadditional lift to the aircraft 300. As depicted, a display unit 332 islocated on the second winglet 338. The location of the display unit 332on the second winglet 338 may be desirable due to the visibility of thesecond winglet 338.

The illustration of the display units 322, 324, 326, 328, 330, and 332on the aircraft 300 in FIG. 3 is only an example of some locations wherethe display units 322, 324, 326, 328, 330, and 332 may be located.Additional display units also may be present on the aircraft 300, butnot seen in this view. For example, a display unit also may be locatedon the first engine 308, the first winglet 336, the other side of thevertical stabilizer 320, or in some other suitable location on theaircraft 300. In yet another example, another display unit may belocated on the other side of the fuselage 306 opposite to the displayunit 324 as seen on the fuselage 306 upon other structures not seen inthis view.

In other illustrative examples, fewer numbers of the display units 322,324, 326, 328, 330, and 332 may be used on the aircraft 300. Forexample, only the display unit 332 on the second winglet 338 and adisplay unit (not shown) on the first winglet 336 may be used. Further,while the display units 322, 324, 326, 328, 330, and 332 may all bepresent on the aircraft 300, not all of the display units 322, 324, 326,328, 330, and 332 may be used substantially concurrently.

In other illustrative examples, the display unit 332 may be seen onmultiple sides of an aircraft structure. For example, the display unit332 may be transparent and display the images 120 on both sidessubstantially concurrently.

Turning now to FIG. 4, an illustration of a portion of the second wing304 of the aircraft 300 with the second winglet 338 is depicted inaccordance with an illustrative embodiment. As depicted, the displayunit 332 on the second winglet 338 is substantially flush to theexterior surface 340 of the aircraft 300.

In particular, the display unit 332 may be constructed to have a shapethat corresponds to the shape for the exterior surface 340 of theaircraft 300 on the second winglet 338 when the display unit 332 is usedon the second winglet 338. The display unit 332 may comprise part of orall of the second winglet 338. In particular, the display unit 332 maybe made as an integral part of the second winglet 338. Morespecifically, the display unit 332 is located on the outboard side 400of the exterior surface 340 of the second winglet 338 of the aircraft300.

In this illustrative example, the display unit 332 displays informationin an image 401. In this illustrative example, the image 401 is in theform of a navigation light 402. In other words, the display unit 332 maydisplay different colors in the image 401 of the navigation light 402 asa navigation aid. For example, the navigation light 402 displayed on thedisplay unit 332 may be a color selected from one of red, white, green,or some other suitable color. Further, the display units 116 in FIG. 1may act as a directional spotlight with or without a mechanical orrefractive lens or may also be used as a flood light.

Further, the navigation light 402 displayed on the display unit 332 alsomay be animated, flashed, strobed, or a combination thereof depending onthe particular implementation. In other illustrative examples, operatingthe navigation light 402 in a strobed or animated manner may providecommunication between aircraft. For example, the aircraft 300 maycommunicate by Morse code or other types of code, symbolic text, or somecombination thereof using the navigation light 402.

The navigation light 402 displayed on the display unit 332 may bedisplayed during various phases of operation of the aircraft. Forexample, the navigation light 402 may be displayed during taxiing,takeoff, ascent, level flight, descent, and landing while aircraft isstationary or moving.

Further, the display unit 332 may change the display to display othertypes of information during other phases of aircraft operation. Forexample, information in the form of advertisements, logos, groundoperations, maintenance and repair information, and other suitable typesof information may be displayed in the form of images and symbols on thedisplay unit 332 when the aircraft 300 is at a gate, in some otherlocation, or in motion. In this example, information may be displayed onthe display unit 332 while the navigation light 402 is operation and/orwhile the navigation light 402 is not operating. In another example, thedisplay unit 332 may function as a directional blinker to indicate aturn for the aircraft 300 in FIG. 3.

Additionally, in some illustrative examples, the display unit 332 may beoriented such that a particular audience may view the display unit 332.The display unit 332 may be dynamically oriented for passengers to viewthe image 401. In other words, the orientation of display unit 332 maychange physically or the image 401 may be displayed in a manner toprovide a desired view of the image 401 at the orientation viewed by thepassengers.

For example, when the aircraft 104 is flying close to the ground orclose to another aircraft, the image 401 in display unit 332 may beoriented such that people on the ground may see the image 401. Theaircraft 104 in FIG. 1 is considered to be close to the ground when aperson on the ground, inside a building, or both is able to view thedisplay unit 332 as clearly as desired. The aircraft 104 is consideredto be close to another aircraft when a person in the second aircraft isable to view the display unit 332 as clearly as desired.

Although the display unit 332 on the second winglet 338 may be locatedon the top of the wing 304 in these illustrative examples, otherorientations for the display unit 332 on the second winglet 338 or on anadditional winglet may be present. For example, the display unit 332 onthe second winglet 338 may be connected to the bottom of the wing 304and be oriented downward.

In other illustrative examples, the display unit 332 on the secondwinglet 338 may be present with an additional display unit on a wingletconnected to the bottom of the wing 304. In other words, the depictedexamples of the display unit 332 on the second winglet 338 do not limitthe orientation or configuration of the display unit 332.

Further, more than one display panel in the display unit 332 may bepresent on the second winglet 338. For example, the display unit 332 mayhave one panel, two panels, five panels, or some other suitable numberof panels in these illustrative examples. As a result, in someillustrative embodiments, images may be displayed on at least one sideof the second winglet 338 or on other winglets of the aircraft 300.

Turning now to FIG. 5, an illustration of another view of a portion ofthe second wing 304 of the aircraft 300 with the second winglet 338 isdepicted in accordance with an illustrative embodiment. As depicted, thedisplay unit 332 on the second winglet 338 is substantially flush to theexterior surface 340 of the aircraft 300.

As can be seen, the display unit 332 is also present on the inboard side500 of the second winglet 338 as well as on the outboard side 400 of thesecond winglet 338 as shown in FIG. 4. In this example, the display unit332 is a two-sided display unit.

As depicted, the display unit 332 displays an image 502 in the form of alogo 504. In other words, the display of the image 502 on the inboardside 500 may be different from the display of the image 401 on theoutboard side 400 of the second winglet 338 in FIG. 4.

In other illustrative examples, another display unit may be used if thedisplay unit 332 is not a two-sided display unit. The particularconfiguration used for displaying information on the second winglet 338may vary depending on the particular implementation.

Further, the display unit 332 on the inboard side of the second winglet338 may also display information to passengers in the aircraft 300during operation of the aircraft 300 or while the aircraft 300 isstationary on the ground. For example, the display unit 332 may displaylocal ground feature information for the aircraft 300. This informationmay be displayed based on a triggering event in triggering events 122 inFIG. 1 such as the activity of passengers, crew, or pilots in theaircraft 300, a particular location of the aircraft 300 that may be ofinterest to the passengers, or based on other trigger events.

Turning now to FIG. 6, an illustration of the tail section 314 of theaircraft 300 in FIG. 3 is depicted in accordance with an illustrativeembodiment. As depicted, the display unit 330 on the vertical stabilizer320 in the tail section 314 of the aircraft 300 in FIG. 3 is mounted tobe substantially flush to the exterior surface 340 of the aircraft 300on the vertical stabilizer 320.

As can be seen in this illustrative example, an image 602 is displayedby the display unit 330 on the vertical stabilizer 320. In thisillustrative example, the image 602 includes a flag 604 and a tailnumber 606. As depicted, the image 602 may be static, dynamic, or acombination thereof. In this illustrative example, the image 602 maydynamically display the flag 604 to show the flag 604 moving as if thewind was passing through the flag 604 in the image 602.

The tail number 606 in the image 602 is a static portion of the image602. Also, the image 602 may be static or dynamic. In other words, theimage 602 may remain the same or may change. For example, the image 602may be animated such as one generated by a computer. When the image 602is dynamic, the image 602 may be changed, additional images may begenerated and displayed in place of the image 602, or some combinationthereof to provide the animation of the flag 604 displayed by thedisplay unit 330.

In other illustrative examples, the image 602 may be video displayed bythe display unit 330 that may change the image 602. In other words, newimages may be displayed in place of, or simultaneous with, the image 602with those images originating from a video. Further, the image 602 alsomay change depending on at least one of the particular locations of theaircraft 300, the phase of flight of the aircraft 300, whether theaircraft 300 is in maintenance or service, whether the aircraft 300 isat a gate or between gates, or based on other conditions or parametersfor the aircraft 300.

Further, in some illustrative examples, the display unit 330 may havemultiple panels that form segments, one panel with multiple segments, orsome combination thereof. In one example, the flag 604 may be displayedon one portion of the display panel in the display unit 330 while thetail number 606 is displayed on another portion of the display panel. Inanother example, the flag 604 may be displayed on one display panel inthe display unit 330 while the tail number 606 is displayed on anotherdisplay panel in the display unit 330. In other illustrative examples,the flag 604 and the tail number 606 may be displayed over multipledisplay panels.

With reference now to FIG. 7, an illustration of another portion of theaircraft 300 in FIG. 3 is depicted in accordance with an illustrativeembodiment. In this illustrative example, a portion of the fuselage 306with the first wing 302 and the second wing 304 is shown with thedisplay unit 324.

In this example, an image 700 is displayed on the exterior surface 340of the aircraft 300 on the fuselage 306 by the display unit 324. In thisexample, the image 700 provides flight information 702 for the aircraft300. In particular, the flight information 702 displayed in the image700 by the display unit 324 is a flight number for the aircraft 300.

Additionally, the display unit 322 on the second wing 304 of theaircraft 300 is shown displaying an image 704. In this example, theimage 704 takes the form of a logo 706 as displayed by the display unit328 on the exterior surface 340 of the aircraft 300.

Further, the display unit 328 on the first wing 302 displays an image708 that also takes the form of a logo 710 as displayed by the displayunit 328 on the exterior surface 340 of the aircraft 300. As can be seenin this illustrative example, the display unit 324 on the fuselage 306is rectangular in shape while the display unit 328 on the first wing 302and the display unit 322 on the second wing 304 are circular in shape.In other words, any shape may be used depending on the particularimplementation.

With reference now to FIG. 8, an illustration of another portion of theaircraft 300 is depicted in accordance with an illustrative embodiment.The display unit 326 is located on nacelle 800 of the second engine 310.An image 802 is displayed on the exterior surface 340 of the aircraft300 by the display unit 326 on the nacelle 800 of the second engine 310.

In this illustrative example, the image 802 takes the form ofinformation that may be used by maintenance personnel or other personnelwhen the aircraft 300 is on the ground. In this particular example, theimage 802 takes the form of a warning 804. The warning 804 may be usedto indicate that that the second engine 310 is about to start, warmingup, or otherwise operating.

In this example, the image 802 is generated in a manner that may beconspicuous or attention-getting with respect to maintenance personnel.For example, the image 802 may be displayed in a color, with animation,or other suitable attention-getting features. For example, when a coloris used, the color of the image 802 may change. In another illustrativeexample, the image 802 may strobe, flash, or include an animated graphicwith a strobe and/or flash feature.

In other illustrative examples, the image 802 may include other types ofinformation. This other type of information may include, for example,without limitation, graphical instructions, text instructions, symbolicinstructions, or some combination thereof that may be animated,scrolling, or stationary, to load cargo or unload cargo. The image 802may indicate classes, types, load status, current weight position,balance load allowables, priorities, or some combination thereof forcargo or the in-aircraft location of the cargo.

As another example, the image 802 may be graphical instructions, textinstructions, symbolic instructions, or some combination thereof thatmay be animated, scrolling, or stationary to fuel the aircraft 300. Inyet another illustrative example, the display of the image 802 mayprovide ground crew with information including destination gateinformation, ‘blinker’ direction indication, confirmation of groundcrew-to-aircrew communication, information regarding needed maintenance,repair, and operations, and other crew-commanded communication. Theseexamples are only illustrative examples of some implementations for thedisplay of the images 120 by the display units 116 in FIG. 1 that may beinitiated by operator 123 such as a crew member or automatically by thecomponents in FIG. 1.

Turning now to FIG. 9, an illustration of a first display unit 900 onthe first horizontal stabilizer 316 and a second display unit 902 on thesecond horizontal stabilizer 318 of the aircraft in FIG. 3 is depictedin accordance with an illustrative embodiment. As depicted, the firstdisplay unit 900 and the second display unit 902 are located on thebottom side of the first horizontal stabilizer 316 and the secondhorizontal stabilizer 318, respectively.

As depicted, the display of the first image 904 displayed on the firstdisplay unit 900 and the second image 906 displayed on the seconddisplay unit 902 may provide information for maintenance personnel. Forexample, the first image 904 and the second image 906 may be indicatorsfor use in precise alignment and guidance of the aircraft 300 during arefueling operation of the aircraft 300.

The illustrative examples in FIGS. 6-9 depict images being displayed onthe exterior surface 340 of the aircraft 300 during different phases ofoperation of the aircraft 300. These phases may include, for example,without limitation, takeoff, level flight, landing, taxiing, refueling,operations while in a stationary position, and other suitable phases ofoperation of the aircraft 300.

With reference now to FIG. 10, an illustration of a cross-sectional viewof the vertical stabilizer 320 of the aircraft 300 taken along the lines10-10 in FIG. 3 is depicted in accordance with an illustrativeembodiment. As depicted, the display unit 330 is substantially flush tothe exterior surface 340 of the aircraft 300 on the vertical stabilizer320.

In this illustrative example, the display unit 330 includes asubstantially transparent protective layer 1000, a display panel 1002, asupport structure 1004, and a power connector 1006. The substantiallytransparent protective layer 1000 is configured to protect the displaypanel 1002 from the environment that may be encountered by the exteriorsurface 340 of the aircraft 300. The power connector 1006 is configuredto provide connection to a power source on the aircraft 300 in FIG. 3.The power connector 1006 may include data and radio frequencyidentifiers.

Turning now to FIG. 11, an exploded perspective view of the display unit330 on the vertical stabilizer 320 on the aircraft 300 in FIG. 3 isdepicted in accordance with an illustrative embodiment. In this depictedexample, the substantially transparent protective layer 1000 may takethe form of a protective lens 1100. The protective lens 1100 may be oneexample of an implementation for substantially transparent protectivelayer 204 shown in block form in FIG. 2. In these illustrative examples,protective lens 1100 may be comprised of glass, a polycarbonate, or someother suitable type of material.

As depicted, the display panel 1002 may take the form of an organiclight-emitting diode display 1102. By using the organic light-emittingdiode display 1102, the display panel 1002 may be fabricated usingvarious materials that may be lighter than with other types of displays.For example, the organic light-emitting diode display 1102 may befabricated on a plastic or metal substrate and may be flexible. Thesupport structure 1004 may be comprised of a composite material, ametal, aluminum, titanium, or some other suitable material depending onthe particular implementation. The support structure 1004 may beintegrated as a contiguous or semi-contiguous load bearing part of theaircraft structure.

With reference now to FIG. 12, an illustration of another implementationfor the display unit 330 on the vertical stabilizer 320 on the aircraft300 in FIG. 3 is depicted in accordance with an illustrative embodiment.In this illustrative example, the display unit 330 may be comprised of asubstantially transparent protective layer 1200 and a display panel1202.

In this illustrative example, a support structure 1204 takes the form ofthe vertical stabilizer 320. As depicted, a recess 1206 may be formed inthe vertical stabilizer 320 and the substantially transparent protectivelayer 1200. The display panel 1202 may be placed into the recess 1206.

As can be seen, the substantially transparent protective layer 1200 issubstantially flush to a surface 1208 of the vertical stabilizer 320. Inthis manner, the display unit 330 forms part of the exterior surface 340on the aircraft 300 with a desired level of aerodynamic performance.

The illustrations of the different locations for the display units 322,324, 326, 328, 330, and 332 on the aircraft 300 in FIGS. 3-12 are onlymeant as some examples of the locations in which components in thedisplay units 322, 324, 326, 328, 330, and 332 on the aircraft 300 inFIG. 3 may be placed on the aircraft 300. Further, the physicalimplementations for components in the display unit 200 illustrated inFIG. 2 in FIGS. 10-12 are also only examples of some implementations ofthe components for the display unit 200 in FIG. 2.

In still other illustrative examples, the recess 1206 may beunnecessary. Instead, the display unit 330 may be sufficiently thin whenconnected to the surface 1208 such that the recess 1206 is not needed toobtain desired aerodynamic performance.

For example, the display unit 330 may be manufactured as part of anappliqué that is placed on the surface 1208. For example, the supportstructure 1204 may be the substrate or layer of material for theappliqué. The display panel 1202 may be an organic light-emitting diodedisplay formed on the layer of material. In this manner, the displayunit 330 may be more easily added to existing aircraft as an aftermarketupgrade, option, or refurbishment. In other illustrative examples, theappliqué may be attached to an aircraft structure of dimension and shapesuch that desired aerodynamic performance is achieved.

With reference next to FIG. 13, an illustration of a block diagram of adisplay unit is depicted in accordance with an illustrative embodiment.Display unit 1300 illustrated in this figure is an example of a displayunit that may be used in the number of display units 116 in the displaysystem 106 for the aircraft 104 in FIG. 1.

As depicted in this particular example, display unit 1300 may be placedin different locations in aircraft 104. For example, display unit 1300may be located in a location selected from an exterior of the aircraft,an interior of the aircraft, a fuselage, a wing, a winglet, a horizontalstabilizer, a vertical stabilizer, an engine housing, a passenger cabin,a cockpit, a galley, or some other suitable location. Display unit 1300may display various types of information selected from at least one of alogo, a trademark, an advertisement, a tail number, safety information,flight information, baggage claim information, ground crew information,gate information, a direction blinker, a navigation light, warninginformation, or some other suitable type of information.

In this illustrative example, the display unit 1300 includes a number ofdifferent components. As depicted, display unit 1300 includes pixels1302, protective layer 1304, and conductive path 1306. In this depictedexample, these different components form display panel 1307 for displayunit 1300. Display unit 1300 may include one or more panels in additionto display panel 1307.

In this illustrative example, a pixel in pixels 1302 is a smallestelement that may be controlled to perform at least one of emitting orreceiving a signal. In particular, a pixel may be a smallest addressbook element that may be controlled to perform at least one of emittingor receiving a signal. For example, pixels 1302 are comprised of atleast one of a light emitting element, a light-emitting diode, anorganic light-emitting diode, a plasma cell, a quantum dot, a liquidcrystal cell, a radio frequency transmitter, an infrared transmitter, anultraviolet light transmitter, or some other suitable device or systemthat may be used as a pixel.

As depicted, protective layer 1304 is associated with pixels 1302. Whenone component is “associated” with another component, the association isa physical association in the depicted examples. For example, a firstcomponent, pixels 1302, may be considered to be physically associatedwith a second component, protective layer 1304, by at least one of beingsecured to the second component, bonded to the second component, mountedto the second component, welded to the second component, fastened to thesecond component, or connected to the second component in some othersuitable manner. The first component also may be connected to the secondcomponent using a third component. The first component may also beconsidered to be physically associated with the second component bybeing formed as part of the second component, extension of the secondcomponent, or both.

In some illustrative examples, pixels 1302 may be associated withprotective layer 1304 by being embedded within protective layer 1304. Inparticular, pixels 1302 may be located inside protective layer 1304 suchthat pixels 1302 are not exposed to the environment around protectivelayer 1304. For example, pixels 1302 may be encapsulated or immersedwithin protective layer 1304. In other illustrative examples, openingsmay be present in protective layer 1304 in areas 1308 where pixels 1302are located in protective layer 1304.

In this illustrative example, protective layer 1304 is substantiallytransparent in areas 1308 over pixels 1302. In this illustrativeexample, protective layer 1304 may be at least one of opaque orsubstantially transparent in another area other than areas 1308 ofpixels 1302.

In this manner, protective layer 1304 may have opaque area 1309 inaddition to substantially transparent areas 1310. In particular, pixels1302 are located in substantially transparent areas 1310 when opaquearea 1309 is present.

In these illustrative examples, opaque area 1309 may be used to provideat least one of aesthetics or information for an aircraft 104 in FIG. 1.For example, opaque area 1309 may include at least one of an image, acolor, text, an applique, or some other suitable visualization thatprovides at least one of aesthetics or information.

Further, protective layer 1304 may be selected from at least one of aflexible layer and a rigid layer. Further, depending on theconfiguration of display unit 1300, protective layer 1304 may bedirectly connected, bonded, glued, or otherwise connected to a portionof aircraft 104 in FIG. 1. The support structure may be the fuselage,cabin wall, or other existing structure in aircraft 104.

In this illustrative example, conductive path 1306 in protective layer1304 performs at least one of cooling or heating for the differentcomponents in display unit 1300. In particular, conductive path 1306 mayperform heating, cooling, or both for pixels 1302. In this illustrativeexample, pixels 1302 are located on conductive path 1306. Pixels 1302are connected to conductive path 1306. In this illustrative example, theconnection may be a thermal connection. The thermal connection allowspixels 1302 to transfer heat with conductive path 1306. In particular,heat may be transferred to or from pixels 1302 using conductive path1306.

Further, in this illustrative example, display unit 1300 also mayinclude circuit system 1311. Circuit system 1311 may be used to controlthe operation of pixels 1302 or to perform other functions in theillustrative example. As depicted, circuit system 1311 includes a numberof circuits 1312. As depicted, the number of circuits 1312 may beencapsulated within protective layer 1304 or otherwise associated withprotective layer 1304 based on the particular implementation. In thisillustrative example, number of circuits 1312 may be selected from atleast one of circuits, integrated circuit chips, a radio frequencyemitter, a light meter, a thermometer, a memory, a processor unit, avideo controller, a conductive path, a trace, or some other suitabletype of circuit.

The number of circuits 1312 are associated with protective layer 1304and connected to conductive path 1306. In this illustrative example, theconnection may be a thermal connection that allows for a transfer ofheat between the number of circuits 1312 and conductive path 1306. Inthis manner, conductive path 1306 also may perform at least one ofheating or cooling for the number of circuits 1312 in circuit system1311.

Additionally, conductive path 1306 also may conduct signals 1314. Withthis use of conductive path 1306, the connection of the number ofcircuits 1312 to conductive path 1306 also may be a connection thatallows for a transfer of signals 1314 between the number of circuits1312 and conductive path 1306. Further, pixels 1302 also may beconnected to conductive path 1306. The connection may be, for example,at least one of an electrical connection, an optical connection, or someother suitable connection.

With the electrical connections, signals 1314 may be used by at leastone of pixels 1302 or circuit system 1311 that are connected toconductive path 1306. In the illustrative example, signals 1314 areselected from at least one of power signals 1316 or data signals 1318.Signals 1314 may be selected from at least one of electrical signals,optical signals or other suitable types of signals that may be receivedand used by at least one of pixels 1302 and circuit system 1311 in theseillustrative examples.

In some illustrative examples, data signals 1318 may be sent from atleast one of pixels 1302 or a number of circuits 1312 in circuit system1311 to a computer or other device located outside of display unit 1300.In this manner, conductive path 1306 may provide a bidirectionaltransfer of data signals 1318. A circuit within circuits 1312 and apixel in pixels 1302 may send signals, receive signals, or both send andreceive signals with respect to each other and other ones of circuits1312 and ones of pixels 1302.

Additionally, protective layer 1304 has surface 1326 that may havetexture 1328. In this illustrative example, texture 1328 may cause adesired airflow over the protective layer. This desired airflow mayprovide a desirable performance such as fuel efficiency or drag foraircraft 104 in FIG. 1. This surface may be formed as part of protectivelayer 1304 or may be another layer placed on protective layer 1304.

The illustration of a display unit 1300 in FIG. 13 is not meant to implyphysical or architectural limitations to the manner in which anillustrative embodiment may be implemented. Other components in additionto or in place of the ones illustrated may be used. Some components maybe unnecessary. Also, the blocks are presented to illustrate somefunctional components. One or more of these blocks may be combined,divided, or combined and divided into different blocks when implementedin an illustrative embodiment.

For example, pixels 1302 perform at least one of receiving signals ortransmitting signals. In particular, when receiving signals, pixels 1302may receive information or act as a sensor. This information received bypixels 1302 may be sent over conductive path 1306 as signals 1314 foruse by computers or other components in aircraft 104 in FIG. 1. Further,pixels 1302 may also transmit signals other than light used to conveyinformation to a human viewer of display unit 1300. In anotherillustrative example, a viewer may be a device such as, for example, avideo camera or a detector. For example, pixels 1302 may also transmitradio frequency signals in addition to or in place of light signals. Inparticular, pixels 1302 may function as an antenna in some illustrativeexamples.

In yet another example, a pixel in pixels 1302 may include circuits aspart of a pixel other than circuits that emit light signals. Forexample, a pixel also may include at least one of a memory, a processorunit, a radio frequency receiver, a battery, a radio frequency emitter,a light meter, a computer clock, a thermometer, or some other suitablecircuit or device in addition to a light emitting diode that emitsvisible light. These components in a pixel may reduce the amount ofother circuits that may be needed in circuit system 1311. For example,the memory may store an internet protocol address for the pixel or for adestination node. The processor may perform operations, includingsending and receiving information.

With reference now to FIG. 14, an illustration of a display unit with acooling system is depicted in accordance with an illustrativeembodiment. As depicted, a display unit 1400 is an example of a displayunit in display units 116 shown in block form in FIG. 1. Morespecifically, a display panel 1401 is one example of the display panel202 in the display unit 200 in FIG. 2. The display unit 1400 may beconfigured to have one display panel or have multiple display panels oneach side of the display unit 1400 in these illustrative examples.Display unit 1400 also may be an example of a physical implementationfor display unit 1300 shown in block form in FIG. 13.

As depicted, the display panel 1401 includes an organic light-emittingdiode display 1402 and a cooling system 1404. The organic light-emittingdiode display 1402 includes a number of light-emitting diodes 1406. Thenumber of light-emitting diodes 1406 may be oriented in a non-normalmanner. In other words, the spacing and/or orientation of the number oflight-emitting diodes 1406 along the plane of the display unit 1400 maybe non-normal in these illustrative examples.

For example, the spacing of the light-emitting diodes in the number oflight-emitting diodes 1406 may be random, where a first pair oflight-emitting diodes is spaced differently than a second pair oflight-emitting diodes. The first pair of light-emitting diodes may becloser together than the second pair of light-emitting diodes. Further,the orientation of the first pair of light-emitting diodes may bedifferent than the orientation of the second pair of light-emittingdiodes in relation to the surface of the display unit 1400.

The cooling system 1404 may be configured to cool the number oflight-emitting diodes 1406. For example, the cooling system 1404 maytransfer heat away from the number of light-emitting diodes 1406 duringoperation of the display panel 1401 to prevent undesired operation ofthe number of light-emitting diodes 1406 due to overheating. In otherillustrative examples, the cooling system 1404 may transfer heat to thenumber of light-emitting diodes 1406 during operation of the displaypanel 1401 to prevent undesired operation of the number oflight-emitting diodes 1406 due to hypothermia.

The cooling system 1404 may be one implementation for the heat transfersystem 134 in FIG. 1 and the heat conductor 214 in FIG. 2. In theseillustrative examples, the cooling system 1404 may include a coolingpath 1408.

The cooling path 1408 may be configured to direct the flow of a coolingfluid 1410 in these illustrative examples. The cooling fluid 1410 maybe, for example, without limitation, at least one of air, nitrogen, agas, a nanofluid, jet fuel, a liquid, water, ethylene glycol, and othersuitable types of cooling fluids. In other illustrative examples, anelectronic cooling device may be located within the cooling path 1408 ormay replace the cooling path 1408. This cooling device may be a peltierdevice in these illustrative examples.

As depicted, cooling path 1408 may be comprised of different types ofcomponents. For example, cooling path 1408 may be a tube or channelconfigured to carry a flow of a cooling fluid. In other examples,cooling path 1408 may be a channel in which a cooling material or acooling device may be located. For example, the cooling path 1408 may becomprised of at least one of aluminum, copper, stainless steel, and someother suitable type of material. In another illustrative example, thecooling path 1408 may also serve as an electrical conductor, groundpath, or both for the number of light-emitting diodes 1406.

While the illustrative embodiments show the number of light-emittingdiodes 1406 with 18 light-emitting diodes, other numbers oflight-emitting diodes may be present in the organic light-emitting diodedisplay 1402. For example, 10 light-emitting diodes, 55, light-emittingdiodes, 2000 light-emitting diodes, or some other number oflight-emitting diodes may be present in the organic light-emitting diodedisplay 1402 depending on the particular implementation. Further, thenumber of light-emitting diodes 1406 in these illustrative examples maybe representative of other types of light-emitting elements such as aplasma element, a liquid crystal display element, or other suitabletypes of light-emitting elements. The illustrative examples are shownfor purposes of illustration and description.

Turning now to FIG. 15, an illustration of a cross-sectional view of adisplay unit with a cooling system is depicted in accordance with anillustrative embodiment. As depicted, a display unit 1400 is an exampleof a display unit in display units 116 shown in block form in FIG. 1.More specifically, the display unit 1400 is seen taken along the lines15-15 in FIG. 14.

In this view, the number of light-emitting diodes 1406 in the organiclight-emitting diode display 1402 in the display panel 1401 are shownwith protective layer 1500. The protective layer 1500 may be one exampleof substantially transparent protective layer 204 shown in block form inFIG. 2.

Further, the number of light-emitting diodes 1406 may have gap 1502. Gap1502 may be a vacuum or may hold a gas, such as an inert gas. In thisillustrative example, gap 1502 is configured to provide insulationbetween the number of light-emitting diodes 1406 and the externalenvironment surrounding the aircraft 104. In some illustrative examples,gap 1502 may be omitted depending on the particular implementation.

In this example, the cooling system 1404 is shown such that the coolingpath 1408 is positioned relative to the rows of the number oflight-emitting diodes 1406. The cooling fluid 1410 flows through thecooling path 1408 to regulate the temperature of the number oflight-emitting diodes 1406. Of course, the cooling path 1408 may havedifferent configurations other than the configuration shown in thisfigure depending on the particular implementation.

With reference now to FIG. 16, an illustration of anothercross-sectional view of a display unit with a cooling system is depictedin accordance with an illustrative embodiment. As depicted, the displayunit 1400 is an example of a display unit in the display units 116 shownin block form in FIG. 1. More specifically, the display unit 1400 isseen taken along the lines 16-16 in FIG. 14. The display unit 1400 iscomprised of two display panels instead of a single display panel inthis illustrative example.

As depicted, the display unit 1400 may have a first side 1600 with afirst display panel 1602 and a second side 1604 with a second displaypanel 1606. A number of light-emitting diodes 1406 is located on thefirst side 1600 and the second side 1604 of the display unit 1400.

A protective layer 1610 may be configured to protect each of the numberof light-emitting diodes 1406. The protective layer 1610 may be oneimplementation for the substantially transparent protective layer 204shown in block form in FIG. 2. Further, the number of light-emittingdiodes 1406 may have gaps 1612.

The cooling system 1404 with the cooling path 1408 and the cooling fluid1410 is shown in this illustrative example. As depicted, the coolingsystem 1404 may control the temperature of the number of light-emittingdiodes 1406 on both first side 1600 and second side 1604 of the displayunit 1400.

In the illustrative examples, the number of light-emitting diodes 1406in FIG. 14 may output distinct wavelengths of light and may comprise ofa cluster of elements, each representing different colors. These colorsinclude, for example, red, green, blue, magenta, cyan, yellow, andwhite.

With reference now to FIG. 17, an illustration of a display unit isdepicted in accordance with an illustrative embodiment. As depicted,display unit 1700 is an example of a physical implementation of adisplay unit in display units 116 shown in block form in FIG. 1.Further, display unit 1700 is an example of a physical implementation ofdisplay unit 1300 shown in block form in FIG. 13. Display unit 1700 maybe used on the exterior or interior of aircraft 104 in FIG. 1.

In this illustrative example, pixels 1702 are associated with protectivelayer 1704. Conductive path 1706 is present and pixels 1702 are locatedon and connected to conductive path 1706 in the illustrative example. Asdepicted, conductive path 1706 is also associated with protective layer1704.

As depicted, conductive path 1706 is configured to provide at least oneof cooling or heating of pixels 1702. Conductive path 1706 includeschannel 1708. In this illustrative example, a cooling or heating fluidmay flow through channel 1708 to provide a heating or cooling function.In one illustrative example, channel 1708 may be omitted from conductivepath 1706.

Additionally, conductive path 1706 also includes trace 1710. Asdepicted, trace 1710 may conduct signals, such as electrical signals.Pixels 1702 are electrically connected to trace 1710 in thisillustrative example.

Turning next to FIG. 18, an illustration of a cross-sectional view of adisplay system is depicted in accordance with an illustrativeembodiment. In this figure, the cross-sectional view of display unit1700 is an example of a cross-section of display unit 1700 taken alonglines 18-18 in FIG. 17.

As depicted, pixels 1702 are encapsulated within protective layer 1704.In this illustrative example, protective layer 1704 provides a structurefor supporting or holding pixels 1702. For example, protective layer1704 may function as a support structure such as support structure 208for display unit 200 in FIG. 2.

In this illustrative example, protective layer 1704 encapsulates pixels1702. As seen in this illustrative example, protective layer 1704 doesnot cover all of trace 1710. Trace 1710 may include one or morecircuits. In particular, protective layer 1704 does not need to cover orencapsulate all of trace 1710.

As depicted, cavities are located adjacent to pixels 1702. Inparticular, cavity 1806, cavity 1808, cavity 1810, cavity 1812, cavity1814, and cavity 1816 are present adjacent to pixel 1818, pixel 1820,pixel 1822, pixel 1824, pixel 1826, and pixel 1828 in pixels 1702,respectively. These cavities may contain air, gas, or may be a vacuumdepending on the particular implementation.

Turning next to FIG. 19, an illustration of another cross-sectional viewof a display unit with a cooling system is depicted in accordance withan illustrative embodiment. In this figure, the cross-sectional view ofdisplay unit 1700 is an example of another implementation for thecross-section of display unit 1700 taken along lines 18-18 in FIG. 17.

As depicted, pixels 1702 are encapsulated within protective layer 1704.In this illustrative example, protective layer 1704 encapsulates pixels1702. As seen in this example, protective layer 1704 also encapsulatesall of trace 1710.

Also shown in this illustrative example are cavities adjacent to pixels1702. In particular, cavity 1906, cavity 1908, cavity 1910, cavity 1912,cavity 1914, and cavity 1916 are present adjacent to pixel 1919, pixel1920, pixel 1922, pixel 1924, pixel 1926, and pixel 1928 in pixels 1702,respectively.

Turning next to FIG. 20, an illustration of another cross-sectional viewof a display unit with a cooling system is depicted in accordance withan illustrative embodiment. In this figure, the cross-sectional view ofdisplay unit 1700 is an example of a cross-section of display unit 1700taken along lines 20-20 in FIG. 17.

In this illustrative example, pixel 2000, pixel 2002 and pixel 2004 inpixels 1702 are located on first side 2006 of conductive path 1706 inprotective layer 1704. As depicted, chip 2008 and chip 2010 are locatedon second side 2012 of conductive path 1706.

The placement of these chips on the opposite side of conductive path1706 from pixels 1702 allows for reducing the space between pixels asopposed to placing the devices on conductive path 1706 on the same sideas pixels 1702. In this manner, the pixel density of display unit 1700may be increased as compared to placing the chips on the same side ofconductive path 1706.

Turning next to FIG. 21, an illustration of another cross-sectional viewof a display unit with a cooling system is depicted in accordance withan illustrative embodiment. In this figure, the cross-sectional view isan example of another implementation for the cross-section of displayunit 1700 in FIG. 20.

In this illustrative example, pixel 2100, pixel 2102, and pixel 2104 inpixels 1702 are located on first side 2106 of conductive path 1706. Chip2108 and chip 2110 are also located on first side 2106 of conductivepath 1706. As depicted, chips or other devices are absent on second side2114 of conductive path 1706.

In this illustrative example, second side 2114 of conductive path 1706does not have pixels or chips or other devices. As a result, thethickness of display unit 1700 may be reduced as compared to theillustrative example shown in FIG. 20. However, the pixel density maynot be as great as when using the implementation shown in FIG. 20.

Turning next to FIG. 22, an illustration of a portion of a display unitis depicted in accordance with an illustrative embodiment. As depicted,portion 2200 of display unit 2202 is an example of a physicalimplementation of a display unit in display units 116 shown in blockform in FIG. 1. Portion 2200 of display unit 2202 also may be an exampleof a physical implementation of display unit 1300 shown in block form inFIG. 13.

In this illustrative example, pixels 2204 are associated with protectivelayer 2206. As depicted, pixels 2204 include pixel 2208, pixel 2210,pixel 2212, pixel 2214, pixel 2216, and pixel 2218. The pixels are shownin phantom because the pixels are located below protective layer 2206.

In this depicted example, protective layer 2206 is substantiallytransparent in areas where the pixels are located. For example,protective layer 2206 is substantially transparent in area 2220, area2222, area 2224, area 2226, area 2228, and area 2230. In thisillustrative example, these areas are substantially transparent suchthat the pixels may transmit or receive light. Another area other thanthe areas where the pixels are located is opaque to form opaque area2232 in this illustrative example.

Opaque area 2232 may have images, color, text, applique, or otheraesthetic or informational elements. For example, the color may be thecolor of a passenger cabin if the display is located in an interior ofan aircraft. If the display is located on the exterior of the aircraft,the color may be the color of the exterior of the aircraft.

In another illustrative example, opaque area 2232 may have a logo orother design on the exterior or interior of the aircraft. In yet anotherillustrative example, opaque area 2232 may have multiple colors.

In this illustrative example, the areas that are substantiallytransparent are substantially the same size as depicted for some of thepixels, such as area 2220 for pixel 2208, area 2222 pixel 2210, area2224 for pixel 2212, and area 2226 for pixel 2214. Further, the areasmay be smaller than the pixel as shown in area 2228 for pixel 2216, andarea 2230 for pixel 2218. In other words, only a portion of a pixel maybe under the substantially transparent area in protective layer 2206 atthe location of the pixel. The other portion of the pixel may be underthe opaque area of protective layer 2206.

The illustration of areas of different sizes in FIG. 22 is shown forpurposes of depicting features of an illustrative example. Whenimplemented in an aircraft, the areas may be of the same size ratherthan different sizes depending on the particular implementation.

The illustrations of display units and cross-sections in FIGS. 14-22 arenot meant to limit the manner in which other illustrative examples maybe implemented. For example, other numbers of pixels may be present inthe display unit. For example, a display unit may have hundreds ofpixels, thousands of pixels, or some other number of pixels. Further,although a particular pattern is shown for the conductive paths, otherpatterns may be used. Also, the conductive path also may not alwaysinclude traces for electrical connections in the different devices.Also, in other illustrative examples, the conductive path may conductlight signals rather than electrical signals for use by at least one ofthe pixels, chips, or other circuits that may be used in a display unit.As yet another example, textures may be used on the surface of theprotective layers.

The different components illustrated in FIGS. 3-22 may be combined withcomponents in FIG. 1, FIG. 2, and FIG. 13 used with the components inFIG. 1, FIG. 2, and FIG. 13, or a combination of the two. Additionally,some of the components in FIGS. 3-22 are illustrative examples of howcomponents shown in block form in FIG. 1, FIG. 2, and FIG. 13 can beimplemented as physical structures.

Further, the illustration of the aircraft 300 and the different displayunits on the aircraft 300 is only an example of one possibleimplementation for the aircraft 104 in FIG. 1 and some possibleimplementations for the display unit 200 in FIG. 2. These illustrationsare not meant to imply limitations to the manner in which other physicalimplementations of the aircraft 104 in FIG. 1 and the display unit 200in FIG. 2 may be implemented.

With reference now to FIG. 23, an illustration of a flowchart of aprocess for displaying the information 114 on the exterior surface 118of the aircraft 104 in FIG. 1 is depicted in accordance with anillustrative embodiment. The process illustrated in this example may beimplemented using the display unit 200 in FIG. 2.

The process begins by identifying the information 114 (operation 2300).The process then displays the information 114 via the display panel 202embedded within the exterior surface 118 of the aircraft 104 (operation2302) with the process terminating thereafter.

Turning now to FIG. 24, an illustration of a flowchart of a process forselecting the image 210 in FIG. 2 using the information 114 in FIG. 1 isdepicted in accordance with an advantageous embodiment. The processillustrated in FIG. 24 may be implemented in the display module 112 inthe computer system 108 in FIG. 1.

The process begins by waiting to receive a triggering event (operation2400). The triggering event may be a triggering event in the triggeringevents 122 in FIG. 1. When a triggering event is received, the processgenerates a number of the images 120 using the information 114 based onthe triggering events 122 (operation 2402). The identification of thenumber of the images 120 depends on the triggering event in theseillustrative examples. The generation of the number of the images 120may be performed by the display module 112. The number of the images 120may be generated by creating new images, selecting pre-existing imagesin the information 114, or some combination thereof.

For example, the number of the images 120 generated may be based on aphase of flight for the aircraft 104. If the aircraft 104 is on thetaxiway, the number of the images 120 may include a logo. If theaircraft 104 is at the gate and maintenance is being performed for thenext flight, the number of the images 120 may include maintenanceinformation. Also, the number of the images 120 also may be based on thelocation of the aircraft 104.

For example, the number of the images 120 may include a logo for a cityat which the aircraft 104 is located. As yet another example, the numberof the images 120 may be selected to include advertisements based on thecity, time of year, weather, local sports affiliations, and other eventsthat may be occurring, as identified by the triggering event that isreceived. The number of the images 120 may be an image that is to bedisplayed by each of the number of the display units 116, or the numberof the images 120 may be a sequence of the images 120 for an animationor video, some combination thereof, or other suitable types of images.

Thereafter, a determination is made as to whether the number of theimages 120 generated replaces a current number of the images 120 beingdisplayed (operation 2404). If the number of the images 120 generatedreplaces the current number of the images 120, the current number of theimages 120 is replaced with the number of the images 120 generated(operation 2406), with the process then returning to operation 2400 asdescribed herein. The replacement of the number of the images 120generated may be performed by the display module 112 sending the numberof the images 120 to appropriate ones of the number of display units116. With reference again to operation 2404, if the number of the images120 generated is the same as the current number of the images 120, theprocess returns to operation 2400.

With reference now to FIG. 25, an illustration of a flowchart of aprocess for displaying information is depicted in accordance with anillustrative embodiment. The process illustrated in FIG. 25 may beimplemented using display unit 200 in FIG. 2 or display unit 1300 inFIG. 13. The display units may be located in at least one of theexterior or interior of an aircraft.

The process begins by sending the information from a number of sourcesto a display unit (operation 2500). The sending of the information inthe number of sources to the display unit may occur by sending datasignals to the display unit. The data signals may be sent through aconductive path in the display unit. Further, power signals also may besent through the conductive path to provide power to the display unit.For example, at least one of information or power may be sent to pixels,circuits, and other devices that may be present in the display unit.

The process displays the information through pixels located in thedisplay unit (operation 2502). The process transfers heat in the displayunit through a conductive path (operation 2504), with the processterminating thereafter. The transfer of heat includes at least one ofcooling or heating the display unit. In this manner, the conductive pathmay provide both a transfer of heat and a transfer of signals with thedisplay unit.

The flowcharts and block diagrams in the different depicted embodimentsillustrate the architecture, functionality, and operation of somepossible implementations of apparatus and methods in an illustrativeembodiment. In this regard, each block in the flowcharts or blockdiagrams may represent a module, segment, function, and/or a portion ofan operation or step. For example, one or more of the blocks may beimplemented as program code, in hardware, or a combination of theprogram code and hardware. When implemented in hardware, the hardwaremay, for example, take the form of integrated circuits that aremanufactured or configured to perform one or more operations in theflowcharts or block diagrams.

In some alternative implementations of an illustrative embodiment, thefunction or functions noted in the blocks may occur out of the ordernoted in the figures. For example, in some cases, two blocks shown insuccession may be executed substantially concurrently, or the blocks maysometimes be performed in the reverse order, depending upon thefunctionality involved. Also, other blocks may be added in addition tothe illustrated blocks in a flowchart or block diagram.

Turning now to FIG. 26, an illustration of a block diagram of a dataprocessing system is depicted in accordance with an illustrativeembodiment. A data processing system 2600 may be used to implementcomputer system 108, the display control system 110, the display module112, and other suitable devices that may be present in the aircraft 104in FIG. 1 or in the aircraft 300 in FIG. 3. In this illustrativeexample, the data processing system 2600 includes a communicationsframework 2602, which provides communications between a processor unit2604, a memory 2606, a persistent storage 2608, a communications unit2610, an input/output unit 2612, and a display 2614. In this example,communication framework may take the form of a bus system.

The processor unit 2604 serves to execute instructions for software thatmay be loaded into the memory 2606. The processor unit 2604 may be anumber of processors, a multi-processor core, or some other type ofprocessor, depending on the particular implementation.

The memory 2606 and the persistent storage 2608 are examples of storagedevices 2616. A storage device is any piece of hardware that is capableof storing information, such as, for example, without limitation, data,program code in functional form, and/or other suitable informationeither on a temporary basis and/or a permanent basis. The storagedevices 2616 may also be referred to as computer readable storagedevices in these illustrative examples. The memory 2606, in theseexamples, may be, for example, a random access memory or any othersuitable volatile or non-volatile storage device. The persistent storage2608 may take various forms, depending on the particular implementation.

For example, the persistent storage 2608 may contain one or morecomponents or devices. For example, the persistent storage 2608 may be ahard drive, a flash memory, a rewritable optical disk, a rewritablemagnetic tape, or some combination of the above. The media used by thepersistent storage 2608 also may be removable. For example, a removablehard or flash drive may be used for the persistent storage 2608.

The communications unit 2610, in these illustrative examples, providesfor communications with other data processing systems or devices. Inthese illustrative examples, the communications unit 2610 is a networkinterface card.

The input/output unit 2612 allows for input and output of data withother devices that may be connected to the data processing system 2600.For example, the input/output unit 2612 may provide a connection foruser input through a keyboard, a mouse, and/or some other suitable inputdevice. Further, the input/output unit 2612 may send output to a printeror other systems. The display 2614 provides a mechanism to displayinformation to a user.

Instructions for the operating system, applications, drivers, and/orprograms may be located in the storage devices 2616, which are incommunication with the processor unit 2604 through the communicationsframework 2602. The processes of the different embodiments may beperformed by the processor unit 2604 using computer-implementedinstructions, which may be located in a memory, such as the memory 2606or using client instruction.

These instructions are referred to as program code, computer usableprogram code, or computer readable program code that may be read andexecuted by a processor in the processor unit 2604. The program code inthe different embodiments may be embodied on different the physical orcomputer readable storage media, such as the memory 2606 or thepersistent storage 2608.

A program code 2618 is located in a functional form on a computerreadable media 2620 that is selectively removable and may be loaded ontoor transferred to the data processing system 2600 for execution by theprocessor unit 2604. The program code 2618 and the computer readablemedia 2620 form a computer program product 2622 in these illustrativeexamples. In one example, the computer readable media 2620 may be acomputer readable storage media 2624 or a computer readable signal media2626. In these illustrative examples, the computer readable storagemedia 2624 is a physical or tangible storage device used to store theprogram code 2618 rather than a medium that propagates or transmits theprogram code 2618.

Alternatively, the program code 2618 may be transferred to the dataprocessing system 2600 using the computer readable signal media 2626.The computer readable signal media 2626 may be, for example, apropagated data signal containing the program code 2618. For example,the computer readable signal media 2626 may be an electromagneticsignal, an optical signal, and/or any other suitable type of signal.These signals may be transmitted over communications links, such aswireless communications links, optical fiber cable, coaxial cable, awire, and/or any other suitable type of communications link.

The different components illustrated for the data processing system 2600are not meant to provide architectural limitations to the manner inwhich different embodiments may be implemented. The differentillustrative embodiments may be implemented in a data processing systemincluding components in addition to and/or in place of those illustratedfor the data processing system 2600. Other components shown in FIG. 26can be varied from the illustrative examples shown. The differentembodiments may be implemented using any hardware device or systemcapable of running the program code 2618.

Illustrative embodiments of the disclosure may be described in thecontext of an aircraft manufacturing and service method 2700 as shown inFIG. 27 and an aircraft 2800 as shown in FIG. 28. Turning first to FIG.27, an illustration of a block diagram of an aircraft manufacturing andservice method is depicted in accordance with an illustrativeembodiment. The components illustrated in FIG. 1 and FIG. 2 may beimplemented during the aircraft manufacturing and service method 2700.During pre-production, the aircraft manufacturing and service method2700 may include specification and design 2702 of the aircraft 2800 inFIG. 28 and a material procurement 2704.

During production, component and subassembly manufacturing 2706 andsystem integration 2708 of the aircraft 2800 in FIG. 28 takes place.Thereafter, the aircraft 2800 in FIG. 28 may go through certificationand delivery 2710 in order to be placed in service 2712. While inservice 2712 by a customer, the aircraft 2800 in FIG. 28 is scheduledfor routine maintenance and service 2714, which may includemodification, reconfiguration, refurbishment, and other maintenance orservice. Upgrades may occur prior to certification and delivery 2710 inthese illustrative examples.

Each of the processes of the aircraft manufacturing and service method2700 may be performed or carried out by a system integrator, a thirdparty, and/or an operator. In these examples, the operator may be acustomer. For the purposes of this description, a system integrator mayinclude, without limitation, any number of aircraft manufacturers andmajor-system subcontractors; a third party may include, withoutlimitation, any number of vendors, subcontractors, and suppliers; and anoperator may be an airline, a leasing company, a military entity, aservice organization, an individual proprietor, and so on.

With reference now to FIG. 28, an illustration of a block diagram of anaircraft is depicted in which an illustrative embodiment may beimplemented. The aircraft 2800 may be one example of the aircraft 104 inFIG. 1 and the aircraft 300 in FIG. 3.

In this example, the aircraft 2800 is produced by the aircraftmanufacturing and service method 2700 in FIG. 27 and may include anairframe 2802 with a plurality of systems 2804 and an interior 2806.Examples of the systems 2804 include one or more of a propulsion system2808, an electrical system 2810, a hydraulic system 2812, and anenvironmental system 2814. Any number of other systems may be included.Although an aerospace example is shown, different illustrativeembodiments may be applied to other industries, such as the automotiveindustry or space industry.

Apparatuses and methods embodied herein may be employed during at leastone of the stages of the aircraft manufacturing and service method 2700in FIG. 27. For example, the display system 106 in FIG. 1 may beimplemented in the aircraft 2800 in FIG. 28 during the specification anddesign 2702 of the aircraft 2800. Further, the display units 116 may bemanufactured during the component and subassembly manufacturing 2706 ofthe aircraft 2800 in FIG. 28. For example, a number of the display units116 may be manufactured as integral parts of the airframe 2802 of theaircraft 2800. In other illustrative examples, a number of the displayunits 116 may be attached to the airframe 2802.

As another example, the display system 106 in FIG. 1 may be added to theaircraft 2800 in FIG. 28 during maintenance and service 2714 of theaircraft 2800. The number of display units 116 in FIG. 1 may be added tothe aircraft 2800 during routine maintenance, refurbishment, upgrades,or other operations performed on the aircraft 2800 during themaintenance and service 2714 of the aircraft 2800. The use of a numberof the different illustrative embodiments may substantially expedite theassembly of and/or reduce the cost of aircraft 2800.

With one or more of the different illustrative embodiments, theinformation 114 may be displayed in the images 120 on the exteriorsurface 118 of the aircraft 104. One or more of the images 120 may bechanged at different times to provide the information 114 that may berelevant or desired for a particular situation or location of theaircraft 104. In this manner, logos and other information may be changedfor the aircraft 104, depending on the phase of flight, location,operator ownership, or other status of the aircraft 104. For example, alogo or advertisement may be in the number of the images 120.

Additionally, a display unit in the display units 116 in FIG. 1 maydisplay any type of images in the images 120. For example, display unit330 may display at least one of a logo, a warning, an advertisement,gate information, baggage information, a tail number, an identificationnumber, a video, or some other suitable image at the same time or atdifferent times. In other words, one of the display units 116 is notlimited to one type of image in the images 120. Further, a display unitin the display units 116 may display any type of information 114suitable for display at a desired location on the aircraft 104. In otherillustrative examples, a display unit in the display units 116 may notdisplay any or certain information at certain times during the operationof the aircraft 104.

Additionally, although the display panels and display units in FIG. 3-9are shown as displaying images 120 on a single side of the display unit,images 120 may also be displayed on multiple sides of a display unit inthe display units 116. These images 120 may be the same images 120 ordifferent images 120 depending on the particular implementation.

Further, safety and maintenance information also may be present in theinformation 114 that is displayed in the images 120. As an example, awarning of an engine start may be present in the images 120, a hazardlocation, a hazard description, and other information may be displayedin the images 120 on the exterior surface 118 of the aircraft 104 invarious locations. As another example, the images 120 also may be usedas navigation lights for the aircraft 104.

Further, the use of the display system 106 on the aircraft 104 mayprovide additional revenue streams for an airline or other operator ofthe aircraft 104 in FIG. 1. For example, billboard logos displayed onthe display units 116 may replace painted or decal effects desired byleasing companies wishing to allocate advertising and logo space on theaircraft 104 in FIG. 1 to multiple airline or individual clients. Inother illustrative examples, the use of the display system 106 on theaircraft 104 may reduce repainting or re-surfacing expenses whenchanging and/or modifying decals, images, or other advertisements.

The description of the different illustrative embodiments has beenpresented for purposes of illustration and description, and is notintended to be exhaustive or limited to the embodiments in the formdisclosed. Many modifications and variations will be apparent to thoseof ordinary skill in the art. Further, different illustrativeembodiments may provide different features as compared to otherillustrative embodiments. The embodiment or embodiments selected arechosen and described in order to best explain the principles of theembodiments, the practical application, and to enable others of ordinaryskill in the art to understand the disclosure for various embodimentswith various modifications as are suited to the particular usecontemplated.

What is claimed is:
 1. An apparatus comprising: pixels; a protectivelayer associated with the pixels, wherein the protective layer issubstantially transparent in areas over the pixels; and wherein theprotective layer has a surface having a texture that causes a desiredairflow over the protective layer; and a conductive path in theprotective layer that transfers heat, wherein the pixels, the protectivelayer, and the conductive path form a display unit for an aircraft. 2.The apparatus of claim 1, wherein the conductive path conducts signalsselected from at least one of power signals or data signals.
 3. Theapparatus of claim 2 further comprising: a number of circuits associatedwith the protective layer and connected to the conductive path.
 4. Theapparatus of claim 3, wherein the conductive path provides the signalsto at least one of the pixels or the number of circuits.
 5. Theapparatus of claim 1, wherein the protective layer is selected from oneof a flexible layer and a rigid layer.
 6. The apparatus of claim 3,wherein at least one of the number of circuits and the pixels areencapsulated within the protective layer.
 7. The apparatus of claim 1,wherein the protective layer has an opaque area in addition to the areasover the pixels that are substantially transparent.
 8. The apparatus ofclaim 7, wherein the opaque area includes at least one of an image, acolor, text, or an applique.
 9. The apparatus of claim 1, wherein thepixels perform at least one of receiving signals and transmitting thesignals.
 10. The apparatus of claim 1, wherein the display unit islocated in a location selected from an exterior of the aircraft, aninterior of the aircraft, a fuselage, a wing, a winglet, a horizontalstabilizer, a vertical stabilizer, an engine housing, a passenger cabin,a cockpit, and a galley.
 11. The apparatus of claim 1, wherein thepixels are comprised of at least one of a light emitting element, alight-emitting diode, an organic light-emitting diode, a plasma cell, aquantum dot, a liquid crystal cell, a radio frequency transmitter, aninfrared transmitter, or an ultraviolet light transmitter.
 12. Theapparatus of claim 3, wherein the number of circuits is selected from atleast one of circuits, integrated circuit chips, a radio frequencyemitter, a light meter, a thermometer, a memory, a processor unit, or avideo controller.
 13. The apparatus of claim 1, wherein the display unitin operation receives information from at least one of a navigationsource, an advertisement database, or a media library.
 14. The apparatusof claim 13, wherein the information is selected from at least one of alogo, a trademark, an advertisement, a tail number, safety information,flight information, baggage claim information, ground crew information,gate information, a direction blinker, a navigation light, or warninginformation, and wherein the information is selected based on a phase offlight of the aircraft.
 15. A method for displaying information, themethod comprising: sending the information from a number of sources to adisplay unit; wherein the display unit comprises a protective layer thathas a surface having a texture that causes a desired airflow over theprotective layer; displaying the information through pixels located inthe display unit; and transferring heat in the display unit through aconductive path.
 16. The method of claim 15, wherein transferring theheat in the display unit through the conductive path comprises:performing at least one of cooling or heating the pixels in the displayunit.
 17. The method of claim 15, wherein sending the information fromthe number of sources to the display unit comprises: sending theinformation from the number of sources in data signals to the displayunit through the conductive path.
 18. The method of claim 15 furthercomprising: sending power signals to the display unit through theconductive path.
 19. The method of claim 15, wherein the display unitincludes circuits connected to the conductive path and furthercomprising: sending at least one of data signals or power signals to thecircuits through the conductive path.
 20. The method of claim 15,wherein the protective layer is selected from one of a flexible layerand a rigid layer.